Preliminary research and technology were performed toward the development of a transpiration cooled inflatable nozzle extension. The J-2 engine of the Saturn-Apollo launch vehicle was selected as a design application test bed to provide realistic operational parameters and a possible hot firing demonstration. The nozzle extension attached at the 27.5 to 1 area ratio of the basic J-2 nozzle exit and extended to an area ratio of 48 to 1. The final nozzle extension design as evolved during this effort utilized conically woven stainless steel airmat as the major construction material. Model and full scale nozzle extensions were fabricated and tested although an actual J-2 hot firing demonstration was not possible due to the lack of a proper altitude test opportunity. (Author)
Investigation of Extendable Nozzle Concepts
1972
123 pages
Report
Keine Angabe
Englisch
Investigation of extendable nozzle concepts
NTRS | 1972
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